introduction to uh-60 cw5 victor figliuolo ops-o / aasf1-ny sp / aasf1-ny sp/ 42 nd cab

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SLIDE - AASF1-NY Standards - 27 Feb 121 Introduction to UH-60

INTRODUCTION to UH-60

CW5 Victor FigliuoloOps-O / AASF1-NY

SP / AASF1-NYSP/ 42nd CAB

ReferencesTM 1-1520-237-10 / CL

Fort Rucker Handout

AASF1-NY

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INTRODUCTION to UH-60OUTLINE

1. Identify the characteristics of the UH-60 Blackhawk Helicopter

2. Identify the UH-60 Fuselage Section Special Features

3. Identify the UH-60 Cockpit Special Features

4. Identify the operational characteristics of the UH-60 Power Train System

5. Identify the operational characteristics of the UH-60 Landing Gear System

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INTRODUCTION to UH-60TERMINAL LEARNING OBJECTIVE:

Identify major components / characteristics of the UH-60 Blackhawk Helicopter

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INTRODUCTION to UH-60LEARNING STEP 1: Identify the characteristics of the UH-60 Blackhawk Helicopter• Army rotary-wing aircraft model designation: UH-60A+/L• Designer and model designation: Sikorsky, S-70• Number and kind of engines: two; General Electric Company

Model T700-GE-701D Turbo shaft• Fully articulated, four-bladed, main rotor head; rigid

crossbeam, canted tail rotor-- two blades, four paddles• Non-retractable landing gear consists of two main gear

assemblies and a tail wheel assembly

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INTRODUCTION to UH-60LEARNING STEP 1: Identify the characteristics of the UH-60 Blackhawk Helicopter

Crew required• Minimum--pilot - copilot• Normal—

Pilot--right side of cockpitCopilot--left side of cockpitCrew chief/gunner--right side forward of cabin

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Mission• Troop assault• Aero-medical evacuation• Aerial recovery• Internal and external cargo

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Aircraft weights• Empty--approximately 11,000 pounds• Design weight--16,825 pounds• Maximum gross weight--22,000 pounds (modified)

Fuel load--approximately 360 gallons, two main tanks full (180 gallons each tank)

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INTRODUCTION to UH-60LEARNING STEP 2: Identify the UH-60 Fuselage Section Special Features

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INTRODUCTION to UH-60LEARNING STEP 2: Identify the UH-60 Fuselage Section Special Features• Primary Structure - The primary structure is aluminum alloy.

Some titanium and steel are used for firewalls and various fittings. Nonstructural members are primarily made of reinforced plastic

• The fuselage may be broken down into the following sections: Nose section, Mid fuselage, Aft fuselage or transition section, Tail cone, Tail Rotor Pylon, Main Rotor Pylon

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Nose or cockpit section• Cockpit canopy, a kevlar reinforced plastic and aluminum

structure• Pilot’s and copilot’s windshields.• Shatter resistant and scratchproof glass• Electrically heated for defogging and anti-icing

• Center windshield- laminated glass, electrically anti-iced

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Nose or cockpit section• Pilot’s and copilot’s cockpit doors

- Aluminum, hinged, and capable of being jettisoned in an emergency

- Contains either a fixed slide-open, or push open vent. The doors that have the push open vent window are designed so the pilot can pull the entire window into the cockpit for egress

• Avionics CompartmentAvionics compartment door hinges up from bottomHeld open in two positions by support strut

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Cabin / Mid Fuselage• Includes crew chief/gunner stations and the troop-cargo

compartment• Two outward facing seats are for the crew chief/gunners.

Crew chief/gunner stations may have machine guns installed• Provisions for a maximum of 12 troop seats.• Provisions for MEDEVAC pedestal with a capacity of four

to six litter patients

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Cabin / Mid Fuselage• Forward sliding crewchief/gunners window incorporates

a nonflammable, stretchplex window split vertically into two panels• Defogged by heater outlet air directed from outer duct

assembly onto window.• Sliding cargo doors on each side that cannot be

jettisoned• Cargo door windows are jettisonable for use as for

emergency exits. Moving the EMERGENCY EXIT handle aft, releases both windows. It may be necessary to push windows free

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Cabin / Mid Fuselage• Emergency Equipment consists of:

- Three first aid kits- Two hand held (portable) fire extinguishers- Crash axe in cabin

• The pilot and copilot flight controls are routed up each side of cabin• The main landing gear struts are mounted on each side

of the helicopter, just aft of the crewchief/gunners windows

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Cabin / Mid Fuselage• Electrical junction boxes and relay panels located in

cabin ceiling• Either a 9.5 Amp Hour Sealed Lead Acid Battery (SLAB) or

a 5.5 Amp Hour Nickel Cadmium (NICAD) battery is located in forward cabin, left-hand side, aft of copilots seat• Cargo floor upper skin, cross-ply, unidirectional

fiberglass; core is Nomex; bottom skin is woven fiberglass. Deck load limit is 300 pounds per square foot.• Cargo hook--8,000 pounds capacity• Two pitot tubes

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Aft Fuselage / Aft Transition Section• Two main fuel tanks #1 on left and #2 on right• Two equipment compartments located above fuel tanks,

20 by 20 by 40 inches, separated by fuel tanks enclosure, maximum capacity is 125 pounds each side. Cargo net restraints are available to restrain equipment

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Aft Fuselage / Aft Transition Section• Auxiliary Power Unit (APU) Hydraulic Accumulator or

Accumulators• Used to start the APU using hydraulic pressure• Normally automatically re-pressurized by the backup

hydraulic pump• The hand pump is used to manually re-pressurize the

APU accumulator if it is below minimum required pressure for APU start or if the APU fails to start

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Aft Fuselage / Aft Transition Section• Steps on outside provide access to engines and APU

above on left and right sides of aircraft

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Tail Cone• The tail cone, interconnecting the transition section and

tail rotor pylon (station 644.62), supports the tail rotor drive shaft and tail pylon• Access panels allow inspection of tail landing gear

attachments, pylon attachment bolts, tail rotor flight control cables and hydraulic lines, and tail landing gear• Tail rotor drive shafts mounted on top under hinged

drives shaft covers

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Tail Rotor Pylon• The tail pylon is supported by and hinged to the tail cone

section which allows folding of the pylon to the right for air transport

- The hinges are not critical structural members, because the tail pylon is secured to the tail cone in the flight position through the use of four bolts- Eight close-tolerance bushings on the tail pylon hinge align with eight tapered pins in the tail cone hinge to ensure proper alignment

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Tail Rotor Pylon• Provides mounting points for the intermediate gearbox,

the connecting drive shaft, the tail gearbox, the tail rotor assembly, the stabilator, and the dual electrical stabilator actuators• The drive shaft cover has a VHF/FM antenna built in to

provide communications, this cover, opens to provide access to the tail drive shaft• Removable fairings on the pylon are provided for access

to the intermediate and tail gear boxes, and tail rotor flight controls

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Tail Rotor Pylon• The trailing edge of the pylon has an aerodynamically

shaped fairing, with a 7 degree camber to help unload tail rotor in forward flight• Retractable telescoping steps / hand-holds allow easy

access to the tail rotor area. Accessed by pushing and rotating the cap 90 degrees counterclockwise, releasing the spring loaded tread, allowing the tread to extend

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Tail Rotor Pylon• The helicopter has a variable angle of incidence

stabilator to enhance handling qualities• Level trim• Optimum attitude for flight

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Main Rotor Pylon

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Main Rotor Pylon• Covers area forward and around main gearbox. Front

area of main rotor pylon slides forward on two tracks; gives access to servos, mixing unit, heater, hydraulic pumps, and various other hydraulic components. Allow smooth airflow induction for cooling aircraft major subsystem components• Steps and walkways aid in inspection and maintenance

of the helicopter. Opening the engine doors and sliding the forward fairing forward reveals additional designated walkways/steps. Designated STEP AREAS have a non skid coating applied

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Main Rotor Pylon• Various types of latches are used to secure fairings,

cowlings, and doors• Aft Main Rotor Pylon fairings hinge open to give access

to APU, transmission oil cooler, two engine fire extinguisher containers/bottles, and the fuel selector valves• Oil Cooler. The oil cooler access panels open to allow

inspection of various fuel lines, piping, valves and oil cooler and blower

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Main Rotor Pylon• Auxiliary Power Unit (APU) is aft and left of main gearbox• Provides pneumatic power for main engine starting

and cabin heating• Electrical power for ground operations and in-flight

emergency electrical power

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Main Rotor Pylon• Onboard Fire Extinguishing System• Controlled by either the pilot or copilot• Both bottles/containers may be used in either main

engine or APU compartment• Thermal discharge indicator on the right side of aft

fuselage will rupture, indicating that one or both containers experienced a thermal discharge

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Main Rotor Pylon• Onboard Fire Extinguishing System

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Main Rotor Pylon• Sliding Access Cover slides forward on two tracks; gives

access to servos, mixing unit, heating system, hydraulic pumps, flight controls, main AC generators, and various other hydraulic components• Heater Mixing Unit is located on the forward right side,

under the sliding main rotor pylon. The heater mixing unit is used to heat the cockpit and cabin and is operated by bleed air from the main engines, APU, or external source

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Main Rotor Pylon• Engine Cowling/Work Platform• The engine compartment doors hinge open, and

provide a flat surface for maintenance use and inspection• Capable of supporting a static weight of 250 pounds

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features• A full set of flight controls for both pilot and co pilot• Energy Absorbing (EA) Pilot Seats are ballistic tolerant

against 7.62 mm rounds

WARNING: Do not store any items below seats. Seats stroke downward during a crash and any obstruction will increase the probability and severity of injury. To prevent injury to personnel, do not release either the normal or emergency vertical adjust levers unless someone is sitting in the seat. The extension springs are under load at all times. With seat at lowest position, the vertical preload on the seat could be as high as 150 pounds. If no one is in the seat and vertical adjust lever (s) is released, the seat will be snapped to the highest stop. Anyone leaning over the seat or with hands on guide tubes above linear bearings, will be seriously injured.

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features• Energy Absorbing (EA) Pilot Seats

NOTE: The seat’s energy attenuators allow the seat to move vertically about 12 inches at between 14 and 19 G’s.

• Emergency Vertical Release Levers allows crewmember to lower the seat to its lowest position• Emergency Tilt Release Levers allows crewmember to tilt

seat aft to remove a disabled pilot• Horizontal and vertical adjustment levers allow seat

adjustment of approximately 5 inches• Armored wing slides forward on outboard side

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features• The NO. 1 AC Primary and DC circuit breaker panels are

located over the copilot's head; the NO. 2 AC Primary, AC Essential and NO. 2 DC Primary circuit breaker panels are located over the pilot's head• The Battery Bus circuit breaker panel is located on the lower

center console on the aft left hand side• The DC Essential Bus circuit breaker panels are located on

the rear of the upper overhead center console

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features• Instrument Panel. Engine and dual flight instruments are

located on the one-piece instrument panel tilted forward 30°. Pilot and copilot instruments on outboard panels with identical layout. Non flight instrument display on center panel• Caution Advisory Panel just to the left of center with 82

indicator capsules. Cautions lights are amber, advisory lights are green• Master Warning Panels one in front of each pilot on the

glare shield contain the following capsules labeled: MASTER CAUTION PRESS TO RESET (amber), #1 ENG OUT, #2 ENG OUT, FIRE, and LOW ROTOR RPM

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features• Vertical Instrument Display System (VIDS) consists of a

vertical strip Central Display Unit (CDU), two vertical strip Pilot Display Units (PDU), and two Signal Data Converters (SDC)• (PDU’s) for both pilots displays the engine power turbine

speed (% RPM 1 and 2), rotor speed (% RPM R), and torque (% TRQ 1 and 2). When the TEST switch is pressed, all PDU scale lamps should light and digital readouts should display 188. Three overspeed lights at the top will appear from left to right when a corresponding rotor speed of 127%, 137%, and 142% is reached

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features• The (CDU) contains instruments that display fuel quantity,

transmission oil temperature and pressure, engine oil temperatures and pressures, turbine gas temperature (TGT), and gas generator speed (Ng) readings. When the Lamp Test Switch is pressed all CDU scale lamps should illuminate and the digital readouts should display 888

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features• The (CDU): • Digital readouts are also installed on the TOTAL FUEL,

TGT, and Ng indicators• The No. 1 and No. 2 fuel quantity is displayed on the

analog scales and the total fuel is displayed on a digital readout• The CDU and PDUs contain photocells that automatically

adjust the lighting of the indicators with respect to ambient light

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features• The (CDU): • A failure of any SDC or CDU processing circuit, display

driver module, or logic power supply, will cause the associated display channel to turn off or switch to the backup processor, and will light the associated CHANNEL failure light• Failure of the lamp power supply within a SDC, will cause

every second display light on the CDU to go off. If a digital processor fails, all digital displays will go off

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features• The Upper Console, overhead between pilot and copilot,

contains engine controls, fire emergency controls, heater and windshield wiper controls, internal and external light controls, electrical systems, and miscellaneous helicopter system controls• The Lower Console, next to the base of the instrument panel

and extending through the cockpit between the pilot and copilot, is easily reached by either pilot. The console is arranged with communication panels, navigational panels, and flight attitude/stability controls

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features• Miscellaneous Switch Panel consists of three push-button

switches marked FUEL IND TEST, TAIL WHEEL, and GYRO ERECT, and one toggle switch marked TAIL SERVO/NORMAL/BACKUP

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features• The FUEL IND TEST SWITCH, when pressed in and held,

causes digital readout and strip indicators to change and caution lights to flash, to test the fuel quantity indicating system• The TAIL WHEEL switch unlocks and locks the TAIL WHEEL in

a trail position, and indicates LOCK or UNLK• The GYRO ERECT initiates a higher voltage to the attitude

indicating system's vertical gyros• TAIL SERVO NORMAL/BACKUP Switch allows selection of #1

or #2 tail rotor servo

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INTRODUCTION to UH-60LEARNING STEP 3: Identify the UH-60 Cockpit Special Features• Stabilator/Automatic Flight Control Panel• The panel contains a MAN SLEW switch, a TEST button,

and AUTO CONTROL RESET switch with a push-to-reset feature.• The automatic flight control portion of the panel controls

the Automatic Flight Control System(AFCS) which enhances the stability and handling qualities of the helicopter.

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INTRODUCTION to UH-60LEARNING STEP 4: Identify the operational characteristics of the UH-60 Power Train System• The UH-60 employs two General Electric T700-GE-700 Turbo

Shaft engines with an input drive shaft that is approximately 18 inches long and connects the engines power turbine output to the input module on main gearbox• The engine is divided into four modules: cold section, hot

section, power turbine section, and accessory section

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INTRODUCTION to UH-60LEARNING STEP 4: Identify the operational characteristics of the UH-60 Power Train System• The main transmission is mounted on top of the cabin

between the two engines• The main transmission assembly consists of five modules

- The Main Module- Two Input Modules

- Two Accessory Modules (drives the following accessories):• The No. 1 & 2 Hydraulic Pump Modules• The No. 1 & 2 AC Generators

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INTRODUCTION to UH-60LEARNING STEP 4: Identify the operational characteristics of the UH-60 Power Train System• Intermediate gearbox is bolted to top of pylon, changes

angle of drive, and reduces RPM• The tail gear box mounts the tail rotor and enables pitch

changes of tail rotor blades, changes angle of drive and gives a gear reduction

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INTRODUCTION to UH-60LEARNING STEP 4: Identify the operational characteristics of the UH-60 Power Train System

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INTRODUCTION to UH-60LEARNING STEP 4: Identify the operational characteristics of the UH-60 Power Train System• Two independent hydraulic systems and a backup hydraulic

system. Backup hydraulic pump is mounted to and driven by an AC electric motor• The automatic flight control system (AFCS) enhances the

stability and handling qualities of the helicopter• The UH60 employs a fully articulated main rotor head• The main rotor hub is machined from titanium forging• Four, non-lubricated, elastomeric, spindle module

assemblies allow hunting, flapping, and pitch change of the four main blades

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INTRODUCTION to UH-60LEARNING STEP 4: Identify the operational characteristics of the UH-60 Power Train System• Tail rotor (XBR) Crossbeam Rotor• The two blade spars bolted together at their centers

make an assembly of four ridged paddles• The counterclockwise rotating tail rotor, canted 20º

upward provides approximately 2.5% lift of gross weight, and allows for:

- Shorter nose- Aft CG capability- Low profile- Greater hover and low speed flight stability

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System• The helicopter has conventional, non-retractable landing

gear system, consisting of two main gear assemblies and a tail wheel assembly• The interchangeable drag beams, attaches to the airframe at

one end and to the shock strut at the other, and transmits landing loads to the airframe and shock strut• A static ground wire is clamped to the left axle retaining bolt

only to assist in dissipating static electricity while on the ground. A static bonding jumper is connected to the airframe and to the drag beam on both main landing gears to ensure there is a good path for any static electricity buildup to the static ground wire connected to the left axle retaining bolt

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System• A landing gear weight-on-wheels (WOW) switch is installed

on the left landing gear to control operation of selected systems• Main shock strut is a two-stage, nitrogen-oil shock strut. It

strokes approximately 24 inches and is covered with a fiberglass panel• Two-stage struts are in tandem. Lower stage compresses

first to absorb shock loads up to 10 feet per second (fps); upper strut starts to compress above 10 fps

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System• Each stage has three variable-size oil chambers and a

floating piston with a nitrogen charge in the struts which gives a spring action as the aircraft lands and taxies; hydraulic fluid (MIL-H-5606) in each stage will regulate the rate of compression and extension• At design weight (16,825 pounds), struts should prevent the

fuselage from contacting the ground when landing at approximately 11.25 g’s

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System• The system incorporates a jack and kneel feature that

permits manual raising or lowering of the fuselage for air transportability• Maximum forward touchdown speed is limited to 60 knots

ground speed on level terrain• Do not exceed a touchdown sink rate of 540 feet-per minute

on level terrain and 360 feet-per minute on slopes with gross weights of up to 16,825 pounds; above 16,825 pounds gross weight 300 feet-per-minute on level terrain and 180 feet-per-minute on slopes

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System• Main Wheel Assembly• Each wheel consists of a 26 x 10.0-11 tubeless tire, that

is serviced with nitrogen, a forged aluminum two section wheel rim (inner diameter -11 inches; outer, 13 inches)• On the inner wheel half, seven (7) drive keys engage the

two rotating steel, key-slotted disks (part of the brake system) to the wheel• Both main wheels have a self-adjusting, double disc,

three-cavity brake assembly, which includes a visual brake lining wear indicator

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System• Brake Assemblies• Has four master cylinders--one on each anti-torque

control pedal• Two slave mixer valves under the pilot’s seat• Parking brake valve under the pilot’s seat• Parking brake T-handle is on the aft center console

NOTE: To set the parking brakes, press on either the pilot or the copilot toe brake pedals, pulling the parking brake handle to its fully extended position, then releasing the toe brakes while holding the handle out

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System• Brake Assemblies• Pressing either pilot or copilot left brake will release the

parking brakes. When releasing the parking brakes with the rotor systems turning, ensure that pressure is applied to both pedals to prevent inadvertently pushing the pedals and changing pitch in the tail rotor blades

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System• Brake housing with wear indicators bolted to each drag

beam• Two visual brake lining wear indicators are located on

both brake housings• The wear indicators are spring loaded in the retracted

position to ensure they do not drag on the disk during normal operation• Pushing on the spring loaded wear indicator pin until it

touches the brake disk then observing the amount of the pin height remaining above the nut indicates the level of wear of the brake pads (pucks). If the wear pin becomes flush with nut, replacement of the brake pads is required

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System• Tail Wheel Assembly• The tail wheel swivels 360° locks in the trail position and

encompasses a two-stage tandem nitrogen-oil shock strut• Lower stage compresses to absorb normal taxi and

landing loads up to 10 feet per second. The upper strut compresses above 10 feet per second• The fixed tail landing gear secures to the rear tail cone

structure and provides rear support of the helicopter. The upper end of the strut is bolted to the tail cone with the lower end of the nitrogen-oil shock strut bolted to the yoke

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System• Tail Wheel Assembly• LANDING SPEED LIMITATIONS - Maximum forward

touchdown speed is limited to 60 knots ground speed on level terrain

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System• Tail Wheel Lock System• An electrically operated actuator, secured to the yoke

assembly, secures the tail wheel in the trailing position when the helicopter is parked or in flight• The lock pin actuator is controlled by the tail wheel lock

control switch in the miscellaneous switch (MISC SW) panel. When the tail wheel control switch is pushed in, power from the DC essential bus energizes the actuator to the extended position which will move the spring cylinder and the lockpin bellcrank aft, inserting the lockpin down into the hole of the fork which prevents the fork from swiveling

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INTRODUCTION to UH-60LEARNING STEP 5: Identify the operational characteristics of the UH-60 Landing Gear System• Tail Wheel Lock System

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INTRODUCTION to UH-60 SUMMARY

1. Identify the characteristics of the UH-60 Blackhawk Helicopter

2. Identify the UH-60 Fuselage Section Special Features

3. Identify the UH-60 Cockpit Special Features

4. Identify the operational characteristics of the UH-60 Power Train System

5. Identify the operational characteristics of the UH-60 Landing Gear System

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QUESTIONS

introduction to uh-60 cw5 victor figliuolo ops-o / aasf1-ny sp / aasf1-ny sp/ 42 nd cab

Documents

ny standards

tankunclassified slide

learning step

operational characteristics

mid fuselage

aft fuselage

blackhawk helicopteridentify

tail rotor pylon